Team 5 D&C QDR Scott Bird Mike Downes Kelby Haase Grant Hile Cyrus Sigari Sarah Umberger Jen Watson November 25, 2003 QDR

Presentation Outline Loiter Endurance Best Angle and Rate of Climb Takeoff Velocity and Ground Roll Turning Rate November 25, 2003 QDR

Method Used to Calculate Endurance Velocity for best endurance at minimum power required V = sqrt[(2*(W/S)/ρ)*(sqrt(K/(3*CD0)))] V = 32.7 ft/s W/S = 1.7714 ρ = 0.0023328 slug/ft K = 1/pi*A*e A = 7 e = 0.8392 CD0 = 0.036 November 25, 2003 QDR

Aircraft Loiter Endurance E = (L_D)*((550*ηp)/(Cbhp*V))*log(Wi/Wf) (Raymer 17.31) L/D = 0.8*L/Dmax Cbhp = 1.570946 lb/(hour/hp) (from mfg. Website) Wi = 49.6 lbs Wf = 43.6 lbs (6 pounds of fuel) E = 51 minutes November 25, 2003 QDR

γ = sin-1([550*bhp*ηp/(V*W) - (D/W)]) (Raymer 17.43) Best Angle of Climb γ = sin-1([550*bhp*ηp/(V*W) - (D/W)]) (Raymer 17.43) The best rate of climb occurs at velocity required at minimum power (same velocity used for best endurance) γ = 28o November 25, 2003 QDR

KT = (T/W) - μg; (Eq. 17.102 in Raymer) Takeoff Ground Roll SG = (1./(2.*g.*KA)).*log((KT + KA.*Vf.^2)./(KT + KA.*Vi.^2)) (17.101 from Raymer) KT = (T/W) - μg; (Eq. 17.102 in Raymer) KA = (ρ./(2.*(W./S))).*(μg.*CL - CD0 - K.*CL.^2); (Eq 17.103 in Raymer) μg = 0.08 for rolling start in wet grass VTO = 36.3 ft/s SG = 50.4 ft ??? (assumptions) November 25, 2003 QDR

Ψ = W*sqrt(n2 – 1)/[(W/g)V] = g*sqrt(n2 – 1)/V (Raymer 17.51) Turning Rate Ψ = W*sqrt(n2 – 1)/[(W/g)V] = g*sqrt(n2 – 1)/V (Raymer 17.51) n = [q/K(W/S)]*[(T/W) – q*CD0/(W/S)] (Raymer 17.53) K = 1/CLα (Raymer 12.57) At cruise V = 50 ft/s and density at 600 feet is 0.0023328 slug/ft3 Ψ = 1.54 rad/sec November 25, 2003 QDR

Make sure that all numbers are current and updated from every sub-team Issues to Address Make sure that all numbers are current and updated from every sub-team Do a reality check on the takeoff ground roll distance Investigate further performance characteristics concerning maneuvers, landing, etc. November 25, 2003 QDR

Questions? Questions? November 25, 2003 QDR

Calculations Re = 432,0000; V = 36.3 ft/s (Takeoff Conditions) Re = 700,000, V = 50 ft/s (Cruise Conditions) November 25, 2003 QDR